Abrégé

A power-generation system includes an electrical system, a turbine engine, and a fluid control system. The turbine engine includes a compressor configured to receive and compress a working fluid, a heat source that transfers heat to the compressed working fluid, a turbine fluidly connected with the compressor to extract work from the heated working fluid and drive rotation of the compressor, and a first heat-exchanger fluidly connected with the turbine to transfer heat away from the heated working fluid to provide a cooled working fluid. The fluid control system fluidly is connected with the electrical system and the turbine engine to circulate the working fluid through the electrical system and the turbine engine.

Classes IPC  ?

• F01K 25/00 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs
• F01K 3/18 - Ensembles fonctionnels caractérisés par l'emploi d'accumulateurs de vapeur ou de chaleur ou bien de réchauffeurs intermédiaires de vapeur comportant des réchauffeurs
• F01K 13/02 - Commande, p. ex. arrêt ou démarrage

Abrégé

A nosecone for a gas turbine engine includes a nosecone body substantially symmetrical around a central axis. The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side to an aft side of the nosecone body. The nosecone further includes an attachment assembly which attaches the nosecone body to the gas turbine engine. The nosecone includes a plurality of airstream protrusions attached to or integral with the nosecone body. A first airstream protrusion of the plurality of airstream protrusions is positioned upstream of a first fan blade to prepare an airstream flowing over the nosecone body for interaction with the first fan blade. The attachment assembly includes a plurality of attachment locations, and a first attachment location of the plurality of attachment locations is collocated with the first airstream protrusion of the plurality of airstream protrusions.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p. ex. rotors

Abrégé

A nosecone for a gas turbine engine includes a nosecone body. The nosecone body is substantially symmetrical around a central axis. The nosecone body includes a side wall which defines a diameter of the nosecone body that increases from a forward side of the nosecone body to an aft side of the nosecone body. The nosecone includes an attachment assembly. The attachment assembly is configured to attach the nosecone body to the gas turbine engine. At least one of the nosecone body or the attachment assembly comprises a tear-resistant fiber.

Classes IPC  ?

• F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction

Abrégé

A turbine engine includes at least one compressor, combustion equipment, and at least one turbine. A stage is positioned aft of the at least one turbine, the stage comprising a plurality of blades. The turbine engine includes an electrical generator. The electrical generator includes a rotor carried on an outer diameter of the plurality of blades of the stage and mechanically rotated by the plurality of blades of the stage, the rotor configured to rotate about a longitudinal axis of the turbine engine, and a stator.

Classes IPC  ?

• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gas turbine engine system includes an enclosure, a compressor assembly located at least partially within the enclosure, and a bleed-duct joint. The compressor assembly includes a compressor and a bleed-air collector having a bleed-air manifold configured to receive a portion of air compressed by the compressor and a bleed-air duct extending through an aperture in the enclosure to direct the portion of the air outside of the enclosure. The bleed-air duct includes a first pipe coupled to the compressor for movement with the compressor and a second pipe extending through the aperture in the first wall and arranged around the first pipe. The bleed-duct joint is configured to couple the bleed-air duct with the enclosure to locate the second pipe relative to the first pipe.

Classes IPC  ?

• F04D 29/54 - Moyens de guidage du fluide, p. ex. diffuseurs
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
• F04D 27/02 - Contrôle de l'emballement
• F04D 29/08 - Joints d'étanchéité

Abrégé

A cyber security data recorder may be provided that includes: a data recorder controller; a data recorder memory; and a data recorder input interface configured to receive a signal from an embedded system. The data recorder controller may read forensic data from the embedded system via the data recorder input interface. The data recorder controller may read samples of the signal at intervals that are random and unknown to the embedded system. Alternatively or in addition, the forensic data may be determined as a rate of jump instructions, a ratio of jump to non-jump instructions, and/or an instruction rate from the signal. The data recorder controller may store the forensic data in the data recorder memory.

Classes IPC  ?

• G06F 21/55 - Détection d’intrusion locale ou mise en œuvre de contre-mesures
• G06F 21/56 - Détection ou gestion de programmes malveillants, p. ex. dispositions anti-virus

Abrégé

A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.

Classes IPC  ?

• F02C 7/26 - DémarrageAllumage
• F02C 7/262 - Redémarrage après extinction
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine

Abrégé

A fan case assembly includes an annular case including a first circumferentially-extending slot formed therein, and a tip treatment segment arranged within the first slot and retained therein. The tip treatment segment includes a radially inwardly-facing segment surface having a tip treatment groove formed therein. The tip treatment segment is selectively removable from and insertable into the first slot and is slidable within and along the first slot such that the tip treatment segment is configured to be selectively positioned within the first slot so as to alter the portion of a flow path across the annular case in order to control stall margin of the gas turbine engine and optimize performance of the gas turbine engine.

Classes IPC  ?

• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
• F04D 29/32 - Rotors spécialement adaptés aux fluides compressibles pour pompes à flux axial
• F01D 5/14 - Forme ou structure
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites

Abrégé

A fan case assembly includes an annular case and a fan track liner. The fan track liner includes a variable wall assembly having a stationary portion defining a circumferentially extending groove therein and a movable segment arranged in the groove. The movable segment can be selectively radially translatable within the groove. Radially inwardly facing surfaces of the movable segment and the stationary portion define a portion of a flow path across the fan track liner, and the movable segment can be radially translated within the groove to alter the portion of the flow path across the fan track liner in order to control stall margin of the engine and optimize performance of the engine.

Classes IPC  ?

• F01D 17/14 - Organes de commande terminaux disposés sur des parties du stator faisant varier l'aire effective de la section transversale des injecteurs ou tuyères de guidage
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A power-generation system includes an electrical system, a turbine engine, and a fluid control system. The turbine engine includes a compressor configured to receive and compress a working fluid, a heat source that transfers heat to the compressed working fluid, a turbine fluidly connected with the compressor to extract work from the heated working fluid and drive rotation of the compressor, and a first heat-exchanger fluidly connected with the turbine to transfer heat away from the heated working fluid to provide a cooled working fluid. The fluid control system fluidly is connected with the electrical system and the turbine engine to circulate the working fluid through the electrical system and the turbine engine.

Classes IPC  ?

• H02K 9/10 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant en circuit fermé, dont une partie est à l'extérieur de l'enveloppe de la machine
• F02C 1/05 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de gaz chauds ou de gaz sous pression non chauffés, comme fluide de travail le fluide de travail étant chauffé indirectement caractérisés par le type ou la source de chaleur, p. ex. utilisant l'énergie nucléaire ou solaire
• F02C 1/10 - Cycles fermés
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines

Abrégé

A fan containment case includes a barrel that includes a case structure and a nanocrystalline metal coating overlying the case structure. The case structure includes a plurality of carbon fiber bands, in which at least an outermost carbon fiber band and an innermost carbon fiber band include a fire resistant polymer matrix. The case structure also includes at least one cut resistant polymer band between the outermost and the innermost carbon fiber bands.

Classes IPC  ?

• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
• F01D 21/04 - Arrêt des "machines" ou machines motrices, p. ex. dispositifs d'urgenceDispositifs de régulation, de commande ou de sécurité non prévus ailleurs sensibles à une position incorrecte du rotor par rapport au stator, p. ex. indiquant cette position

Abrégé

A gas turbine engine system includes an enclosure, a compressor located within the disclosure, and a bleed-air collector coupled to the compressor. The compressor includes an outer case and a bleed-air valves fluidly coupled with the outer case of the compressor and configured to direct a portion of the air through the outer case. The bleed-air collector is fluidly coupled to the bleed-air valve and includes a bleed-air manifold configured to collect the portion of the air bled from the primary flow path and a first bleed-air duct fluidly coupled to the first bleed-air manifold to receive the collected bleed air and direct the first portion of the air through one of the plurality of walls and out of the enclosure.

Classes IPC  ?

• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

An exhaust nozzle includes an outer nozzle case having an outer surface and an inner surface, a nozzle plug, and a thrust reverser coupled to the outer nozzle case and including a first thrust reverser panel coupled to the outer nozzle case and an actuator system coupled with the first thrust reverser panel and configured to move the first thrust reverser panel between and including a stored configuration and a reverse-thrust configuration. In the stored configuration, the first thrust reverser panel and a portion of the actuator system provide a portion of an exterior surface of the exhaust nozzle.

Classes IPC  ?

• F02K 1/60 - Inversion du jet principal par blocage de l'échappement vers l'arrière à l'aide d'éléments pivotants ayant la forme de paupières ou de coquilles, p. ex. inverseurs du type se trouvant en aval de la sortie de la tuyère en position de fonctionnement
• F02K 1/76 - Commande ou régulation des inverseurs de poussée

Abrégé

Systems and methods for fluid flow control are provided. A coarse valve and a fine valve are connected in parallel in a conduit. A coarse valve controller controls the coarse valve in a feedback loop in which an error signal is feedback to the coarse valve controller and a coarse valve setting is an output of the coarse valve controller. The error signal is a difference between the property of the fluid flow and a set point. The coarse valve controller operates as a proportional-integral controller. A fine valve controller controls the fine valve in the same feedback loop as the coarse valve controller. The fine valve controller has a center-seeking control scheme and operates as a proportional controller or a proportional-integral controller depending on whether the coarse valve setting is in a saturation range.

Classes IPC  ?

• F02C 7/057 - Commande ou régulation
• F02C 9/16 - Commande du débit du fluide de travail
• G05D 7/06 - Commande de débits caractérisée par l'utilisation de moyens électriques

Abrégé

A turbine engine includes at least one turbine, combustion equipment, and at least one compressor. The at least one compressor includes a compressor stage. The compressor stage includes a plurality of compressor blades configured to input work into a core airflow flowing through the turbine engine. The turbine engine includes an electrical generator. The electrical generator includes a rotor carried on an outer diameter of the plurality of compressor blades of the compressor stage and mechanically rotated by the plurality of compressor blades of the compressor stage and configured to rotate about a longitudinal axis of the turbine engine. The electrical generator further includes a stator.

Classes IPC  ?

• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines

Abrégé

An aircraft includes a duct system, a gas turbine engine, and an inlet flow regulation system. The duct system includes a main duct, a first inlet duct in fluid communication with the main duct, and a second inlet duct in fluid communication with the main duct. The inlet flow regulation system includes an inlet flow regulator configured to manage different flow characteristics of a flow of air entering the first and second inlet ducts to form a substantially uniform flow distribution through the main duct and into the gas turbine engine and a control unit in communication with the inlet flow regulator and configured to selectively move the inlet flow regulator.

Classes IPC  ?

• F01D 17/00 - Régulation ou commande par variation de flux
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 9/20 - Commande du débit du fluide de travail par étranglementCommande du débit du fluide de travail par réglage des aubes

Abrégé

A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and a valve seal configured to block bleed air from passing between the piston and the manifold when the piston is in a closed position.

Classes IPC  ?

• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

A test apparatus for a ceramic matrix composite (CMC) component. The test apparatus includes a first support member configured to mechanically support a CMC component from a first side. The CMC component includes a T-joint and a pinhole. The test apparatus includes a second support member configured to mechanically support the CMC component from a second side opposite the first side. The first support member and the second support member are configured to be forced toward each other to cause the CMC component to fail at the pinhole and not at the T-joint.

Classes IPC  ?

• G01N 3/08 - Recherche des propriétés mécaniques des matériaux solides par application d'une contrainte mécanique par application d'efforts permanents de traction ou de compression

Abrégé

A turbine engine includes a core section comprising at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine; a core vane assembly coupled to the core section, wherein the core vane assembly comprises a plurality of core vanes configured to modify core fluid flow; a fan connected to the core section and configured to be rotated by the at least one turbine, rotation of the fan providing thrust to a vehicle that includes the turbine engine; and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor, wherein the electrical generator comprises: a rotor mechanically rotated via the fan or a shaft that is rotationally coupled to the fan, wherein the rotor rotates about the longitudinal axis; and a stator.

Classes IPC  ?

• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance

Abrégé

An example aircraft includes a plurality of gas-turbine engines mounted external to a fuselage of the aircraft, each gas-turbine engine of the plurality of gas-turbine engines including a respective hydraulic pump of a plurality of hydraulic pumps; a hydraulic motor disposed within the fuselage of the aircraft; a hydraulic distribution network configured to carry hydraulic fluid between the hydraulic motor and the plurality of hydraulic pumps to drive the hydraulic motor; and an electrical generator disposed within the fuselage of the aircraft and configured to be driven by the hydraulic motor.

Classes IPC  ?

• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• B64D 27/14 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz à l'intérieur des fuselages ou fixés à ceux-ci
• F15B 1/04 - Accumulateurs
• F15B 1/26 - Réservoirs d'alimentation ou de pompage
• F15B 11/17 - Systèmes de servomoteurs dépourvus d'asservissement avec plusieurs servomoteurs utilisant plusieurs pompes
• F15B 15/18 - Ensembles combinés comportant moteur et pompe

Abrégé

An example method includes pressurizing, by a plurality of engine driven hydraulic pumps respectively attached to a plurality of gas-turbine engines of an aircraft, hydraulic fluid; generating, by a hydraulic motor disposed within a fuselage of the aircraft and using combined pressurized hydraulic fluid received from the plurality of engine driven hydraulic pumps, rotational mechanical energy; and generating, by an electrical generator disposed within the fuselage of the aircraft and using the rotational mechanical energy, electrical energy.

Classes IPC  ?

• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 27/40 - Aménagements pour le montage de groupes moteurs sur aéronefs

Abrégé

A method includes receiving, by a computing device, a raw image indicative of a cross-section of a thermally-sprayed layer. The image includes a matrix of pixels, and each respective pixel in the matrix of pixels defines a luminance value. The method may further include determining, based on the luminance values, at least one pixel that corresponds to an oxide component in the layer and removing the at least one pixel that corresponds to the oxide component in the layer to generate a modified matrix of pixels. The method may further include generating an oxide-filtered image based on the modified matrix of pixels. The method may further include converting, by the computing device and based on the luminance values, the oxide-filtered image into a binary image and determining, by the computing device and based at least partially on the binary image, a porosity of the coating layer.

Classes IPC  ?

• G01N 15/08 - Recherche de la perméabilité, du volume des pores ou de l'aire superficielle des matériaux poreux
• G06T 5/20 - Amélioration ou restauration d'image utilisant des opérateurs locaux
• G06T 7/13 - Détection de bords
• G06V 10/60 - Extraction de caractéristiques d’images ou de vidéos relative aux propriétés luminescentes, p. ex. utilisant un modèle de réflectance ou d’éclairage
• H04N 23/76 - Circuits de compensation de la variation de luminosité dans la scène en agissant sur le signal d'image

Abrégé

A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer includes a microstructure. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value. The method includes determining, by the computing device and based on the luminance values of the matrix of pixels, a quantification of a layering of the microstructure of the thermally-sprayed layer.

Classes IPC  ?

• G06T 7/00 - Analyse d'image
• G06T 5/92 - Modification de la plage dynamique d'images ou de parties d'images basée sur les propriétés globales des images
• G06T 7/60 - Analyse des attributs géométriques
• G06V 10/24 - Alignement, centrage, détection de l’orientation ou correction de l’image
• G06V 10/77 - Traitement des caractéristiques d’images ou de vidéos dans les espaces de caractéristiquesDispositions pour la reconnaissance ou la compréhension d’images ou de vidéos utilisant la reconnaissance de formes ou l’apprentissage automatique utilisant l’intégration et la réduction de données, p. ex. analyse en composantes principales [PCA] ou analyse en composantes indépendantes [ ICA] ou cartes auto-organisatrices [SOM]Séparation aveugle de source

Abrégé

A method includes receiving, by a computing device, an image indicative of a cross-section of a thermally-sprayed layer. The thermally-sprayed layer defines a porosity comprising a void volume of the thermally-sprayed layer. The image comprises a matrix of pixels, each pixel in the matrix of pixels defining a respective luminance value of a plurality of luminance values. The method includes identifying, based on the luminance values, at least one pixel that is indicative of a void volume in the thermally-sprayed layer. The method includes calculating, based on the at least one pixel that is indicative of the void volume in the thermally-sprayed layer, a total porosity of the thermally-sprayed layer. The method includes determining, by the computing device and based on the at least one pixel that corresponds to a void volume in the thermally-sprayed layer, a quantification of a spatial homogeneity of the porosity of the thermally-sprayed layer.

Classes IPC  ?

• G01N 15/08 - Recherche de la perméabilité, du volume des pores ou de l'aire superficielle des matériaux poreux
• C23C 4/06 - Matériaux métalliques
• G06V 10/60 - Extraction de caractéristiques d’images ou de vidéos relative aux propriétés luminescentes, p. ex. utilisant un modèle de réflectance ou d’éclairage

Abrégé

A multi-piece heat exchanger for transferring heat between a hot working fluid and a coolant according to the disclosure includes a multi-piece shell, a core, and first and second expansion joints. The multi-piece shell is arranged around an axis and receives coolant therein. The core is located within the shell and direct a hot working fluid therethrough.

Classes IPC  ?

• F28F 9/02 - Boîtes de distributionPlaques d'extrémité

Abrégé

A multi-piece radial turbine rotor includes a hub and a bladed crown manufactured via additive layer manufacturing. A bond is formed between the hub and the bladed crown to fix the components together for rotation.

Classes IPC  ?

• F04D 29/28 - Rotors spécialement adaptés aux fluides compressibles pour pompes centrifuges ou hélicocentrifuges
• F04D 17/00 - Pompes à flux radial spécialement adaptées aux fluides compressibles, p. ex. pompes centrifugesPompes hélicocentrifuges spécialement adaptées aux fluides compressibles
• F04D 29/02 - Emploi de matériaux spécifiés
• F04D 29/58 - RefroidissementChauffageRéduction du transfert de chaleur

Abrégé

A heat exchanger for transferring heat between a hot working fluid and a coolant according to the disclosure includes a shell, a core, and an expansion joint. The shell is arranged around an axis and receives a coolant therein. The core is located within the shell and directs a hot working fluid therethrough.

Classes IPC  ?

• F28F 9/02 - Boîtes de distributionPlaques d'extrémité

Abrégé

An example electric machine of a gas-turbine engine having a longitudinal axis includes a stator; a rotor configured to rotate around the stator and about the longitudinal axis of the gas-turbine engine, the rotor comprising: a rotor body having an inner surface and an outer surface; and magnets on the inner surface of the rotor body, wherein axial edges of the magnets perpendicular to the longitudinal axis are profiled to include a shoulder that corresponds to a geometry of a radial retention structure of the rotor.

Classes IPC  ?

• H02K 1/2791 - Aimants montés en surfaceAimants sertis
• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• H02K 1/28 - Moyens de montage ou de fixation des parties magnétiques tournantes sur ou aux structures constituant le rotor
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 21/22 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant autour des induits, p. ex. volants magnétiques

Abrégé

An electric machine of a gas-turbine engine, the electric machine comprising: a stator; and a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets; and one or more retention rings attached to the rotor body and configured to radially retain the magnets to the inner surface of the rotor body.

Classes IPC  ?

• H02K 1/2786 - Rotors externes
• F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
• H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p. ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
• H02K 7/14 - Association structurelle à des charges mécaniques, p. ex. à des machines-outils portatives ou des ventilateurs

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an atomization system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• B22F 9/08 - Fabrication des poudres métalliques ou de leurs suspensionsAppareils ou dispositifs spécialement adaptés à cet effet par des procédés physiques à partir d'un matériau liquide par coulée, p. ex. à travers de petits orifices ou dans l'eau, par atomisation ou pulvérisation
• B01D 1/00 - Évaporation
• B01D 1/18 - Évaporation par pulvérisation pour obtenir des solides secs
• G01H 17/00 - Mesure des vibrations mécaniques ou des ondes ultrasonores, sonores ou infrasonores non prévue dans les autres groupes de la présente sous-classe

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a cold spray system performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• G01N 29/44 - Traitement du signal de réponse détecté
• B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive
• C23C 24/04 - Dépôt de particules par impact

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a fluid transport process possessing a plurality of process attributes. The fluid transport process may include a flow of a fluid along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• G01N 29/024 - Analyse de fluides en mesurant la vitesse de propagation ou le temps de propagation des ondes acoustiques
• G01N 29/46 - Traitement du signal de réponse détecté par analyse spectrale, p. ex. par analyse de Fourier

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an additive manufacturing system performing a process possessing a plurality of process attributes. The process includes depositing material by interaction of an energy beam and a material stream on a build target to form a structure. The system includes a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may further include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• B29C 64/386 - Acquisition ou traitement de données pour la fabrication additive
• B29C 64/209 - TêtesBuses
• B29C 64/268 - Agencements pour irradiation par faisceaux laserAgencements pour irradiation par faisceaux d’électrons [FE]
• B29C 64/321 - Alimentation
• B33Y 50/00 - Acquisition ou traitement de données pour la fabrication additive

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by a system performing a powder transport process possessing a plurality of process attributes. The powder transport process may include a flow of a powder stream along at least one path. The system may further include a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum. Each process attribute of the plurality of process attributes may be associated with at least one respective frequency band. The computing device may include a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• G01N 29/44 - Traitement du signal de réponse détecté

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an engine performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• G01N 29/44 - Traitement du signal de réponse détecté
• F02D 41/22 - Dispositifs de sécurité ou d'avertissement en cas de conditions anormales

Abrégé

An example system includes at least one acoustic sensor configured to generate at least one time-dependent acoustic data signal indicative of an acoustic signal generated by an nuclear power plant performing a process possessing a plurality of process attributes, and a computing device including an acoustic data signal processing module configured to receive the at least one time-dependent acoustic data signal, and transform the at least one time-dependent acoustic data signal to a frequency-domain spectrum, wherein each process attribute of the plurality of process attributes is associated with at least one respective frequency band, and a correlation module configured to determine a process attribute of the plurality of process attributes by identifying at least one characteristic of the frequency-domain spectrum.

Classes IPC  ?

• G01N 29/14 - Recherche ou analyse des matériaux par l'emploi d'ondes ultrasonores, sonores ou infrasonoresVisualisation de l'intérieur d'objets par transmission d'ondes ultrasonores ou sonores à travers l'objet utilisant des techniques d'émission acoustique
• G01N 29/34 - Génération des ondes ultrasonores, sonores ou infrasonores
• G01N 29/44 - Traitement du signal de réponse détecté
• G01N 29/46 - Traitement du signal de réponse détecté par analyse spectrale, p. ex. par analyse de Fourier

Abrégé

A system includes a hydrogen fuel delivery system for an engine that pumps hydrogen from a tank in a liquid state and an evaporator configured to convert at least some of the hydrogen to a gaseous state. The system includes a heat source thermally coupled with the system and fluidly uncoupled from the system. The system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen. The system further includes a coolant loop that circulates coolant between the heat source and the evaporator. The coolant loops includes a valve that splits the coolant flowing from the evaporator into a first portion that flows to a heater and a second portion that flows to the heat source. The first and second portions are directed to the evaporator after having passed through the heater and the heat source.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur

Abrégé

A method includes creating a first image of a software system, creating a second image of the software system including a second code level layout different than the first code level layout, verifying and validating the first and second images of the software system, certifying the first and second images, deploying the first image of the software system on a first operating system, and automatically detecting a first cyberattack being executed on the first image of the software system operating in the first operating system. In response to detecting the first cyberattack being executed on the first image of the software system operating on the first operating system, deploying the second image of the software system on the first operating system in order to disrupt the first cyberattack on the first image of the software system.

Classes IPC  ?

• G06F 21/55 - Détection d’intrusion locale ou mise en œuvre de contre-mesures
• G06F 16/11 - Administration des systèmes de fichiers, p. ex. détails de l’archivage ou d’instantanés
• G06F 21/64 - Protection de l’intégrité des données, p. ex. par sommes de contrôle, certificats ou signatures

Abrégé

The present disclosure teaches a turbine-powered system with a thermoelectric cooler configured to selectively cool powered electronics in the system. In examples provided, the thermoelectric cooler including a cooling plate coupled to the powered electronics and a heat sink integrated into aero surfaces of a gas turbine engine.

Classes IPC  ?

• F01D 25/12 - Refroidissement

Abrégé

A vane assembly adapted for a gas turbine engine includes a first vane segment that extends circumferentially about an axis and a second vane segment. The second vane segment includes a band that extends circumferentially about the axis and a plurality of vanes coupled to the band and extending radially from the band.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

A thermal system includes a tank storing a cooling fluid in a liquid state and a gas state, a first heat exchanger releasing heat into the tank, a second heat exchanger fluidly downstream of the fluid storage tank and exchanging heat between the cooling fluid and a heat load, a turbine fluidly downstream of the second heat exchanger and extracting mechanical energy from the cooling fluid, and a combustor fluidly upstream of the turbine and fluidly downstream of the second heat exchanger. The cooling fluid that has been heated by the second heat exchanger passes through the first heat exchanger and thereby heats upstream cooling fluid resident in the fluid storage tank, and the combustor is configured to ignite the cooling fluid flowing from the second heat exchanger such that combusted cooling fluid flows through and drives the turbine.

Classes IPC  ?

• F01K 25/10 - Ensembles fonctionnels ou machines motrices caractérisés par l'emploi de fluides énergétiques particuliers non prévus ailleursEnsembles fonctionnant selon un cycle fermé, non prévus ailleurs utilisant des vapeurs particulières ces vapeurs étant froides, p. ex. ammoniac, gaz carbonique, éther
• F01K 3/02 - Emploi d'accumulateurs et de machines motrices d'un type particulierLeur commande
• F01K 3/16 - Disposition commune de l'accumulateur et du réchauffeur
• F01K 9/02 - Aménagements ou modifications des pompes à condensats ou à air
• F01K 27/00 - Ensembles fonctionnels transformant la chaleur ou l'énergie d'un fluide en énergie mécanique, non prévus ailleurs
• F17C 7/04 - Vidage des gaz liquéfiés avec changement d'état, p. ex. vaporisation

Abrégé

A vane assembly includes an outer case, a plurality of vanes, and an inner body assembly. The outer case defines an outer boundary of a flow path of the vane assembly. The plurality of vanes extend radially inward from the outer case relative to a central axis. The inner body assembly is configured to secure the plurality of vanes radially relative to the central axis. The inner body assembly includes an inner case arranged circumferentially about the central axis, a band coupled with the inner case, and a retainer ring that extends into the band and into each of the plurality of vanes.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur

Abrégé

An airfoil adapted for use in a gas turbine engine includes a base and an airfoil body that extends radially outward from the base relative to an axis to a tip of the airfoil body. The airfoil body has a leading edge, a trailing edge, a suction side, and a pressure side. The airfoil body is formed to include notches that extend into the airfoil body to reduce a weight of the airfoil.

Classes IPC  ?

• F01D 5/14 - Forme ou structure

Abrégé

A multi-piece radial turbine rotor includes a hub, a plurality of turbine blades, and a flowpath ring that couples the turbine blades to the hub. The flowpath ring is coupled with each of the plurality of turbine blades and the hub to locate the flowpath ring radially between the hub and each of the plurality of turbine blades. The flowpath ring is formed to include a plurality of apertures spaced apart from one another about the flowpath ring and extending radially through the flowpath ring. Each of the plurality of apertures receives a corresponding one of the plurality of turbine blades therein. The hub is fixed to the flowpath ring by a friction weld joint and each of the plurality of turbine blades is fixed to the flowpath ring by a blade joint.

Classes IPC  ?

• F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
• B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
• F01D 5/02 - Organes de support des aubes, p. ex. rotors
• F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

An example system includes an electrical machine electrically configured to generate electrical energy used by one or more components of a gas-turbine engine; an energy storage system; and a controller electrically connected to the energy storage system and configured to receive electrical energy from the energy storage system, wherein, in response to the gas-turbine engine being shut off, the controller is configured to cause the electrical machine to rotate a rotor of the gas-turbine engine using the energy received from the energy storage system.

Classes IPC  ?

• B64D 31/00 - Systèmes de commande des groupes moteursAménagement de systèmes de commande des groupes moteurs sur aéronefs
• B60L 50/52 - Propulsion électrique par source d'énergie intérieure au véhicule utilisant de la puissance de propulsion fournie par des batteries ou des piles à combustible caractérisée par des moteurs à courant continu
• B64D 27/02 - Aéronefs caractérisés par le type ou la position des groupes moteurs
• B64D 27/10 - Aéronefs caractérisés par le type ou la position des groupes moteurs du type à turbine à gaz
• B64D 27/24 - Aéronefs caractérisés par le type ou la position des groupes moteurs utilisant la vapeur ou l'énergie de ressorts
• H02J 7/00 - Circuits pour la charge ou la dépolarisation des batteries ou pour alimenter des charges par des batteries
• H02K 7/00 - Dispositions pour la mise en œuvre d'énergie mécanique associées structurellement aux machines dynamo-électriques, p. ex. association structurelle avec des moteurs mécaniques d'entraînement ou des machines dynamo-électriques auxiliaires
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 11/33 - Circuits d’entraînement, p. ex. circuits électroniques de puissance

Abrégé

A power-generation system includes an electrical system, a turbine engine, and a pump. The turbine engine includes a compressor configured to receive and compress a working fluid, a heat source that transfers heat to the compressed working fluid, a turbine fluidly connected with the compressor to extract work from the heated working fluid, and a first heat-exchanger fluidly connected with the turbine to transfer heat away from the heated working fluid to provide a cooled working fluid. The pump conducts a portion of the cooled working fluid from the first heat-exchanger to the electrical system to cool components of the electrical system.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 9/10 - Dispositions de refroidissement ou de ventilation par un agent de refroidissement gazeux circulant en circuit fermé, dont une partie est à l'extérieur de l'enveloppe de la machine

Abrégé

A fan case assembly adapted for use with a gas turbine engine includes a fan casing and a bleed air flow control system. The fan casing includes an annular case and a fan track liner coupled with the annular case. The bleed air flow control system is configured to bleed selectively a portion of air flowing through a gas path of the fan case assembly for use as a cooling source in the fan case assembly.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
• F04D 29/58 - RefroidissementChauffageRéduction du transfert de chaleur

Abrégé

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Classes IPC  ?

• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
• F01D 17/12 - Organes de commande terminaux disposés sur des parties du stator
• F02C 9/16 - Commande du débit du fluide de travail
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales

Abrégé

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine. The exhaust nozzle includes a thrust reverser configured to be retained by the inner plug.

Classes IPC  ?

• F02K 1/60 - Inversion du jet principal par blocage de l'échappement vers l'arrière à l'aide d'éléments pivotants ayant la forme de paupières ou de coquilles, p. ex. inverseurs du type se trouvant en aval de la sortie de la tuyère en position de fonctionnement
• F02K 1/76 - Commande ou régulation des inverseurs de poussée

Abrégé

A system includes a hydrogen fuel delivery system for an engine. The hydrogen fuel delivery system includes a pump configured to pump hydrogen from a tank storing the hydrogen in a liquid state through the hydrogen fuel delivery system, and an evaporator configured to convert at least some of the hydrogen in the liquid state to a gaseous state. The system also includes a heat source thermally coupled with the hydrogen fuel delivery system and fluidly uncoupled from the hydrogen fuel delivery system. The hydrogen fuel delivery system is configured to supply the hydrogen to the engine for combustion and cool the heat source using the hydrogen.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 7/224 - Chauffage du combustible avant son arrivée au brûleur

Abrégé

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section includes a low pressure turbine that drives a low pressure spool that rotates about a longitudinal axis of the turbine engine, a high pressure turbine that drives a high pressure spool, and a compressor rotated by the high pressure spool. The fan is connected to the low pressure spool and rotated by the low pressure spool. Rotation of the fan may provide thrust to a vehicle that includes the turbine engine. The electrical generator is positioned between the fan and the compressor. The electrical generator comprises a rotor concentric with and rotated via the low pressure spool, the rotor configured to rotate about the longitudinal axis, and a stator positioned radially within the rotor and configured to electromagnetically interact with the rotor to generate power.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• B64D 27/35 - Aménagements pour la production, la distribution, la récupération ou le stockage d'énergie électrique à bord

Abrégé

A gas turbine engine includes a combustor and a valve coupled to the combustor. The valve includes a valve body, a valve stem, and an actuator. The valve body is formed to define an air chamber. The valve stem is movable between a closed position and an open position. The actuator is configured to move selectively the valve stem between the closed position and the open position.

Classes IPC  ?

• F16K 31/126 - Moyens de fonctionnementDispositifs de retour à la position de repos actionnés par un fluide le fluide agissant sur un diaphragme, un soufflet ou un organe similaire
• F16K 1/36 - Corps de soupapes

Abrégé

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

Classes IPC  ?

• F01D 5/30 - Fixation des aubes au rotorPieds de pales
• F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
• F01D 5/32 - Verrouillage, p. ex. par des aubes terminales de verrouillage ou par des clavettes
• F01D 1/08 - "Machines" ou machines motrices à déplacement non positif, p. ex. turbines à vapeur avec des moyens stationnaires de guidage de fluide de travail et un rotor à ailettes ou de structure analogue traversées par le fluide de travail principalement dans le sens radial à action centripète

Abrégé

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include an axially-extending lug features for coupling the ceramic matrix composite turbine blades to a central hub.

Classes IPC  ?

• F01D 5/32 - Verrouillage, p. ex. par des aubes terminales de verrouillage ou par des clavettes
• F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion

Abrégé

Various aspects of the techniques are directed to a turbine engine comprising a core section, a fan, and an electrical generator. The core section comprises at least one compressor and at least one turbine that both rotate about a longitudinal axis of the turbine engine, wherein the at least one turbine drives at least one spool, and an oil sump positioned to collect oil used to lubricate rotational elements for one or more of the at least one compressor and the at least one turbine. The fan rotated by the at least one spool. The electrical generator integrated into the core section and positioned outside of the oil sump, wherein the electrical generator comprises a rotor rotated via the at least one spool about the longitudinal axis, and a stator configured to electromagnetically interact with the rotor to generate power.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F02C 6/20 - Aménagements des ensembles fonctionnels de turbines à gaz pour l'entraînement des véhicules
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 21/22 - Moteurs synchrones à aimants permanentsGénératrices synchrones à aimants permanents avec des induits fixes et des aimants tournants avec des aimants tournant autour des induits, p. ex. volants magnétiques

Abrégé

An example electric machine includes a rotor and a stator. The stator includes a stator core defining a longitudinal axis and a plurality of stator end windings extending from the stator core along the longitudinal axis. Adjacent end windings of the plurality of stator end windings define a radial gap, and the radial gap is configured to allow a cooling fluid to flow within the radial gap and in contact with the adjacent stator end windings.

Classes IPC  ?

• H02K 1/20 - Parties fixes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
• H02K 15/08 - Exécution des enroulements par pose des conducteurs dans ou autour des parties formant le noyau

Abrégé

An example electric machine of a gas-turbine engine includes a stator; a rotor configured to rotate around the stator, the rotor comprising: a rotor body having an inner surface and an outer surface; magnets on the inner surface of the rotor body, the magnets having an inner surface and an outer surface; and a retention band on the inner surface of the magnets and configured to retain the magnets to the rotor body.

Classes IPC  ?

• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 1/2791 - Aimants montés en surfaceAimants sertis

Abrégé

A bleed valve assembly includes a manifold coupled to a case of a compressor of a gas turbine engine to control a flow of bleed air exiting the compressor, a valve housing coupled with the manifold, a piston configured to move selectively relative to the valve housing and the manifold, and one or more shims located between the valve housing and the piston.

Classes IPC  ?

• F04D 27/02 - Contrôle de l'emballement

Abrégé

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and a tip clearance system. The tip clearance system includes a tip clearance sensor located in an annular plenum defined between an inner case and an outer case included in the case assembly. The tip sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Classes IPC  ?

• F01D 11/24 - Réglage actif du jeu d'extrémité des aubes par refroidissement ou chauffage sélectifs d'éléments du stator ou du rotor
• F01D 17/02 - Aménagement des éléments sensibles
• G01B 21/16 - Dispositions pour la mesure ou leurs détails, où la technique de mesure n'est pas couverte par les autres groupes de la présente sous-classe, est non spécifiée ou est non significative pour mesurer la distance ou le jeu entre des objets espacés

Abrégé

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a axis, a second ring arranged circumferentially around the axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

Classes IPC  ?

• F02K 1/82 - Parois des tubulures de jet, p. ex. chemises

Abrégé

A turbine assembly includes a bladed rotor mounted for rotation about an axis of the gas turbine engine, a case assembly, and an actively-cooled tip clearance system. The tip clearance system includes a tip clearance sensor located radially outward of an inner case of the case assembly. The actively-cooled tip clearance system includes a sensor is configured to monitor a tip clearance formed between the bladed rotor and the case assembly during operation of the gas turbine engine.

Classes IPC  ?

• F01D 11/20 - Réglage actif du jeu d'extrémité des aubes
• F01D 11/00 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages

Abrégé

A vortex particle separator adapted for use with a gas turbine engine includes a vortex tube, a plurality of swirl vanes, and an outlet tube. The vortex tube receives atmospheric air laden with particles. The plurality of swirl vanes are arranged within the vortex tube and separate the atmospheric air into a first flow of air having the particles and a second flow of air that is relatively free of the particles. The outlet tube extends into the vortex tube to define a scavenge passageway between the outlet tube and the vortex tube that receives the first flow of air. The outlet tube defines an intake passageway that receives the second flow of air. The vortex particle separator further includes a layer of material having a low coefficient of restitution on at least one of an interior surface of the vortex tube and a surface of the swirl vanes.

Classes IPC  ?

• F02C 7/052 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction comportant des dispositifs pour empêcher la pénétration d'objets ou de particules endommageantes comportant des dispositifs séparateurs de poussière
• B01D 45/16 - Séparation de particules dispersées dans des gaz ou des vapeurs par gravité, inertie ou force centrifuge en utilisant la force centrifuge produite par le mouvement hélicoïdal du courant gazeux
• B04C 3/00 - Appareils dans lesquels la direction axiale du tourbillon ne change pas

Abrégé

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Classes IPC  ?

• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F01D 17/12 - Organes de commande terminaux disposés sur des parties du stator
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales
• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor

Abrégé

A cooling system may comprise a vapor cycle system. The cooling system may comprise a gas turbine engine. The vapor cycle system may include a compressor, a heat exchanger downstream from the compressor, and a heat load downstream from the heat exchanger and upstream of the compressor. The cooling system may comprise a bleed air conduit. The bleed air conduit may be configured to receive bleed air from the gas turbine engine. The cooling system may comprise a bleed turbine driven by the bleed air supplied from the bleed air conduit. The bleed turbine may be configured to drive the compressor of the vapor cycle system. The compressor may be connected to a bleed turbine via a shaft. The cooling system may comprise a throttle valve to control a flow of the bleed air through the bleed air conduit.

Classes IPC  ?

• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F02C 3/10 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur avec une autre turbine entraînant un arbre de sortie mais n'entraînant pas le compresseur
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

A stator housing assembly includes a stator housing and a stator sleeve. The stator sleeve including a combination of composite layers with different high strength fibers. The stator housing includes a first end section and a second end section that define a stator cavity configured to contain a pressurized cooling fluid. The stator sleeve defines a longitudinal axis and includes a plurality of layers of composite materials that include more than one high strength fiber material. High strength fibers may include carbon and glass fibers. Portions of the stator sleeve may have different combinations of high strength fiber materials and fiber orientations to optimize sleeve properties.

Classes IPC  ?

• H02K 1/18 - Moyens de montage ou de fixation des parties magnétiques fixes sur ou aux structures constituant le stator
• H02K 1/04 - Détails du circuit magnétique caractérisés par le matériau employé pour l'isolation du circuit magnétique ou de parties de celui-ci
• H02K 1/20 - Parties fixes du circuit magnétique avec des canaux ou des conduits pour l'écoulement d'un agent de refroidissement
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H02K 15/12 - Imprégnation, chauffage ou séchage des bobinages, des stators, des rotors ou des machines
• F02C 7/00 - Caractéristiques, parties constitutives, détails ou accessoires non couverts dans, ou d'un intérêt plus général que, les groupes Entrées d'air pour ensembles fonctionnels de propulsion par réaction

Abrégé

An example propulsion engine includes at least one radial support structure (RSS) radially disposed about an engine centerline. A power cable is at least partially contained within a cavity of a first RSS or a cavity fluidically coupled to the cavity of the first RSS. The first RSS defines at least one cooling aperture fluidically coupling the cavity of the first RSS to an exterior surface of the first RSS. The at least one cooling aperture is configured to allow cooling fluid to flow into or out of the cavity of the first RSS to cool the power cable.

Classes IPC  ?

• F01D 15/10 - Adaptations pour la commande des générateurs électriques ou combinaisons avec ceux-ci
• F01D 9/06 - Conduits d'admission du fluide à l'injecteur ou à l'organe analogue
• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F02C 7/32 - Aménagement, montage ou entraînement des auxiliaires
• H01B 7/42 - Conducteurs ou câbles isolés caractérisés par la forme avec des dispositions pour la dissipation ou la conduction de la chaleur
• H02K 7/18 - Association structurelle de génératrices électriques à des moteurs mécaniques d'entraînement, p. ex. à des turbines
• H05K 9/00 - Blindage d'appareils ou de composants contre les champs électriques ou magnétiques
• F01D 25/12 - Refroidissement
• F02C 6/00 - Ensembles fonctionnels multiples de turbines à gazCombinaisons d'ensembles fonctionnels de turbines à gaz avec d'autres appareilsAdaptations d'ensembles fonctionnels de turbines à gaz à des applications particulières
• F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
• H01B 9/00 - Câbles de transport d'énergie

Abrégé

A radial turbine rotor incorporating ceramic matrix composite turbine blades is disclosed. The radial turbine rotor can include a dovetail shape retention features for coupling the ceramic matrix composite turbine blades to a central hub.

Classes IPC  ?

• F01D 5/32 - Verrouillage, p. ex. par des aubes terminales de verrouillage ou par des clavettes
• F01D 5/28 - Emploi de matériaux spécifiésMesures contre l'érosion ou la corrosion
• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

A method of monitoring a fuel system in a gas turbine engine. The method may comprise pumping fuel to a combustor from a fuel tank with a pump. The method may comprise controlling a flow of the fuel to the combustor with a metering valve disposed downstream of the pump and closing a spill valve disposed downstream of the pump, wherein the spill valve is closed in fixed increments and closing the spill valve increases a pressure in the fuel system. The method may comprise opening a pressure valve in response to the pressure in the fuel system being equal to or greater than a predetermined value, and capturing a degree of closing of the spill valve when the pressure valve opens.

Classes IPC  ?

• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 7/22 - Systèmes d'alimentation en combustible
• F02C 7/26 - DémarrageAllumage
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor

Abrégé

A method of mitigating uncommanded or uncontrollable high thrust in a gas turbine engine is provided. The method may comprise pumping fuel to a combustor from a fuel tank, controlling a flow rate of the fuel to the combustor with a metering valve, spilling a portion of the fuel pumped by the pump with a primary spill valve, controlling a pressure of the fuel flowing to the combustor via a pressure valve, detecting a pressure differential across the pressure valve with a pressure transducer, determining the flow rate of the fuel based on the detected pressure differential and the positional feedback of the pressure valve opening, comparing the determined flow rate with a demand flow rate, and opening a secondary spill valve when the determined flow rate exceeds the demand flow rate.

Classes IPC  ?

• F02C 9/26 - Commande de l'alimentation en combustible
• F02C 9/28 - Systèmes de régulation sensibles aux paramètres ambiants ou à ceux de l'ensemble fonctionnel, p. ex. à la température, à la pression, à la vitesse du rotor
• F02C 7/22 - Systèmes d'alimentation en combustible

Abrégé

A gas turbine engine includes a bypass duct, a rotating detonation augmentor, and a flow valve. The bypass duct is configured to conduct air through a flow path arranged around an engine core of the gas turbine engine. The rotating detonation augmentor is located in the bypass duct and configured to be selectively operated to detonate fuel and a portion of the air to increase thrust for propelling the gas turbine engine. The flow valve is configured to vary selectively the portion of the air flowing into the rotating detonation augmentor to control a magnitude of the thrust increase provided by the rotating detonation augmentor during operation of the rotating detonation augmentor.

Classes IPC  ?

• F02K 3/02 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion

Abrégé

A propulsion unit includes a gas turbine engine and an exhaust nozzle coupled to an aft end of the gas turbine engine. The exhaust nozzle is configured to interact with exhaust gases exiting the gas turbine engine in an aft direction. The exhaust nozzle includes an outer nozzle case and an inner plug that cooperate to define an exhaust flow path therebetween. The exhaust nozzle is configured to manipulate the exhaust gases to provide different thrust capabilities for the gas turbine engine.

Classes IPC  ?

• F02K 1/60 - Inversion du jet principal par blocage de l'échappement vers l'arrière à l'aide d'éléments pivotants ayant la forme de paupières ou de coquilles, p. ex. inverseurs du type se trouvant en aval de la sortie de la tuyère en position de fonctionnement
• F02K 1/76 - Commande ou régulation des inverseurs de poussée

Abrégé

A rotor assembly includes a first rotor arranged circumferentially about a central axis. A second rotor is arranged circumferentially about the central axis and couples to the first rotor for rotation therewith. A balance weight is located in a space radially between the first rotor and the second rotor.

Classes IPC  ?

• F01D 5/02 - Organes de support des aubes, p. ex. rotors

Abrégé

Various aspects of the techniques are directed to a turbine engine that includes a core section comprising a compressor and a turbine that both rotate about a longitudinal axis of the turbine engine. The turbine engine also includes a fan comprising radially distributed blades, the fan connected to the core section and configured to be rotated by the turbine, and an electrical generator integrated into the core vane assembly and positioned in the core section aft of the fan and fore of the at least one compressor. The electrical generator comprises a stator, a turbine configured to extract work from a core fluid flow, the turbine configured to rotate about the longitudinal axis, and a combined rotor rotationally coupled to the fan, the combined rotor formed from a single component that incorporates a blade retainer for retaining at least one of the plurality of radially distributed blades.

Classes IPC  ?

• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F02C 7/36 - Transmission de puissance entre les différents arbres de l'ensemble fonctionnel de turbine à gaz, ou entre ce dernier et l'utilisateur de puissance

Abrégé

A gas turbine engine includes a bypass duct including an outer wall, a flow wall arranged within the bypass duct so as to bifurcate a flow path of the bypass duct into radially outer and inner flow paths, and a heat exchanger. The outer wall includes a segmented wall portion that is removable from the outer wall. The heat exchanger is arranged within the radially outer flow path and is coupled to the segmented wall portion such that the heat exchanger is configured to be removed from the bypass duct via removal of the segmented wall portion from the outer wall.

Classes IPC  ?

• F02C 7/12 - Refroidissement des ensembles fonctionnels
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

A heat-exchanger assembly includes a shroud, a heat exchanger, and a mounting system. The shroud is configured to direct a flow of air through the heat-exchanger assembly. The heat exchanger is configured to transfer heat. The mounting system is configured to couple the shroud with the heat exchanger.

Classes IPC  ?

• F01D 25/12 - Refroidissement
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations

Abrégé

A gas turbine engine includes a bypass duct and a heat-exchanger assembly. The bypass duct is configured to direct air through a flow path. The heat-exchanger assembly is configured to receive a first portion of the air flowing through the flow path of the bypass duct and to divert a second portion of the air flowing through the flow path around the heat-exchanger assembly.

Classes IPC  ?

• F01D 25/00 - Parties constitutives, détails ou accessoires non couverts dans les autres groupes ou d'un intérêt non traité dans ces groupes
• F01D 9/04 - InjecteursLogement des injecteursAubes de statorTuyères de guidage formant une couronne ou un secteur
• F01D 25/14 - Carcasses d'enveloppe modifiées à cet effet

Abrégé

A gas turbine engine including an auxiliary compressor for pressuring cooling air delivered to turbine section components is disclosed. The auxiliary compressor is configured to increase the pressure of compressed air received from a primary compressor prior to movement of the compressed air to cooling air passageways of the turbine system.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02C 3/04 - Ensembles fonctionnels de turbines à gaz caractérisés par l'utilisation de produits de combustion comme fluide de travail ayant une turbine entraînant un compresseur
• F23R 3/00 - Chambres de combustion à combustion continue utilisant des combustibles liquides ou gazeux

Abrégé

A system for detecting a failure in a thermocouple array may comprise the thermocouple array. The thermocouple array may comprise a plurality of thermocouples. The system may comprise an impedance determination circuit. The impedance determination circuit may include a capacitor that has a capacitance equal to an expected capacitance of one of the plurality of thermocouples. The one of the plurality of thermocouples may be connected to test nodes of the impedance determination circuit. The system may comprise a comparator circuit connected to the impedance determination circuit, where the comparator circuit includes an amplifier and a comparator. The system may comprise an excitation circuit connected to the impedance determination circuit, where the excitation circuit includes a waveform generator and an amplifier.

Classes IPC  ?

• G01K 15/00 - Test ou étalonnage des thermomètres
• G01K 7/026 - Dispositions pour signaler la défaillance ou la déconnexion de thermocouples
• G01K 1/02 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres
• G01K 7/02 - Mesure de la température basée sur l'utilisation d'éléments électriques ou magnétiques directement sensibles à la chaleur utilisant des éléments thermo-électriques, p. ex. des thermocouples
• G01K 13/08 - Thermomètres spécialement adaptés à des fins spécifiques pour mesurer la température de corps solides en mouvement en mouvement rotatif

Abrégé

A method of monitoring a health of a temperature system may comprise selecting a temperature sensor of a plurality of temperature sensors arranged in an array, where each temperature sensor corresponds to an address within the array. The method may comprise identifying the address corresponding to the single temperature sensor, sending the address to a multiplexer, and selecting the single temperature sensor using the identified address. The method may comprise testing the selected single temperature sensor calculating an average temperature detected by the plurality of temperatures sensors.

Classes IPC  ?

• G01K 7/026 - Dispositions pour signaler la défaillance ou la déconnexion de thermocouples
• G01K 1/02 - Moyens d’indication ou d’enregistrement spécialement adaptés aux thermomètres
• G01K 15/00 - Test ou étalonnage des thermomètres

Abrégé

A bypass duct assembly for a gas turbine engine includes a bypass duct, a heat exchanger assembly, and an inlet cowl. The bypass duct is configured to direct bypass air around an engine core of the gas turbine engine. The heat exchanger assembly includes a heat exchanger located in the bypass duct and configured to transfer heat to the bypass air. The inlet cowl is coupled with the bypass duct and the heat exchanger assembly.

Classes IPC  ?

• F02K 3/075 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux commande du rapport des débits des différents flux
• F02C 6/08 - Ensembles fonctionnels de turbines à gaz délivrant un fluide de travail chauffé ou pressurisé à d'autres appareils, p. ex. sans sortie de puissance mécanique délivrant des gaz comprimés le gaz étant prélevés sur le compresseur de la turbine à gaz
• F02C 7/14 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F02K 3/06 - Ensembles fonctionnels comportant une turbine à gaz entraînant un compresseur ou un ventilateur soufflant dans lesquels une partie du fluide énergétique passe en dehors de la turbine et de la chambre de combustion l'ensemble fonctionnel comprenant des soufflantes carénées, c.-à-d. des soufflantes à fort débit volumétrique sous basse pression pour augmenter la poussée, p. ex. du type à double flux comprenant une soufflante avant
• F02K 3/115 - Chauffage du flux dérivé à l'aide d'un échange indirect de chaleur
• F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes

Abrégé

A gas turbine engine includes a bypass duct, an inlet cowl, and a heat-exchanger assembly. The bypass duct is configured to direct air through a flow path to provide thrust to propel the gas turbine engine. The inlet cowl is located in the bypass duct and configured to collect a portion of the air flowing in the bypass duct. The heat-exchanger assembly is removably coupled with the inlet cowl and configured to receive the portion of the air from the inlet cowl.

Classes IPC  ?

• F02C 7/28 - Agencement des dispositifs d'étanchéité
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gas turbine engine includes a bypass duct including an outer wall, a heat exchanger arranged within the bypass duct, and a turnbuckle assembly. The outer wall includes a main body and an access panel removably coupled to the main body. The turnbuckle assembly couples the heat exchanger to the access panel, and includes a first rod coupled to the access panel and a second rod coupled to the first rod and to the heat exchanger. The outer end of the first rod is threadably received in a socket of a socket housing removably coupled to the access panel such that the first rod is fixedly coupled to the socket housing to increase lateral stiffness of the heat exchanger and the turnbuckle assembly such that the lateral dynamic mode is outside of a fan rotor operating range.

Classes IPC  ?

• F02C 7/20 - Montage ou bâti de l'ensemble fonctionnelDisposition permettant la dilatation calorifique ou le déplacement
• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air

Abrégé

A gas turbine engine includes a heat exchanger and an inlet shroud. The heat exchanger is configured to transfer heat. The inlet shroud is configured to be coupled with the heat exchanger upstream of the heat exchanger.

Classes IPC  ?

• F02C 7/141 - Refroidissement des ensembles fonctionnels des fluides dans l'ensemble fonctionnel du fluide de travail

Abrégé

A method of assembling a radial turbine rotor includes manufacturing turbine blades, a flowpath ring, and a hub. The method includes fixing the turbine blades circumferentially around the flowpath ring by a blade joint between the turbine blades and the flowpath ring to form a ring assembly. The method includes spinning the hub and moving the hub into engagement with the flowpath ring to locate the hub radially inwardly of the flowpath ring and to form a hub joint between the flowpath ring and the hub.

Classes IPC  ?

• B23P 15/00 - Fabrication d'objets déterminés par des opérations non couvertes par une seule autre sous-classe ou un groupe de la présente sous-classe
• F01D 5/02 - Organes de support des aubes, p. ex. rotors
• F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
• F01D 5/08 - Dispositifs de chauffage, de protection contre l'échauffement ou de refroidissement
• F01D 5/30 - Fixation des aubes au rotorPieds de pales

Abrégé

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Classes IPC  ?

• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F04D 27/02 - Contrôle de l'emballement
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales

Abrégé

A system includes a gas turbine engine configured to provide propulsion to an aircraft and a starter system configured to start the gas turbine engine. The starter system comprises a motor controller and a closed-loop cooling system configured to cool the motor controller during an emergency in-flight restart operation of the gas turbine engine. The closed-loop cooling system includes a cooling fluid reservoir containing cooling fluid. The cooling fluid is configured to receive thermal energy from the motor controller during the emergency in-flight restart operation of the gas turbine engine.

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• F02C 7/12 - Refroidissement des ensembles fonctionnels

Abrégé

An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising: a first air-turbine starter, the first air-turbine starter configured to rotate a spool of the first gas-turbine engine; and a first electric starter, the first electric starter configured to rotate the spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, during a time period, the first-air turbine starter and the first electric starter to start the first gas-turbine engine while the aircraft is on the ground; measure, during the time period, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

Classes IPC  ?

• F02C 7/262 - Redémarrage après extinction
• F02C 7/275 - Entraînement du rotor pour le démarrage mécanique

Abrégé

A starting apparatus for a gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes a fuel supply system, a combustor, and a controller. The controller is configured to cause fuel to be introduced to the combustor of the gas turbine engine at a first threshold rotational speed of the gas-turbine engine during a normal starting operation in which the aircraft is on the ground. The controller is configured to cause fuel to be introduced to the combustor at a second threshold rotational speed of the gas-turbine engine during an emergency in-flight restarting operation in which the aircraft is in-flight. The second threshold rotational speed is lower than the first threshold rotational speed. Introducing fuel at the second threshold rotational speed results in a higher temperature in a turbine of the gas turbine engine than introducing fuel at the first threshold rotational speed.

Classes IPC  ?

• F02C 7/26 - DémarrageAllumage
• F02C 9/46 - Commande de secours de l'alimentation en combustible

Abrégé

A starting apparatus for a first gas turbine engine of a plurality of gas turbine engines of an aircraft. The apparatus includes an air turbine starter, an electric machine, and a controller. The controller is configured to receive an emergency restart command for the first gas turbine engine while the aircraft is in-flight, determine whether the first gas turbine engine is in operation, determine whether at least a second gas turbine engine of the plurality of gas turbine engines is in operation, and, responsive to receiving the emergency restart command and determining that at least the second gas turbine engine of the plurality of gas turbine engines is in operation and that the first gas turbine engine is not in operation, perform an emergency restart of the first gas turbine engine.

Classes IPC  ?

• F02C 7/26 - DémarrageAllumage
• F02C 7/268 - Entraînement du rotor pour le démarrage
• F02C 7/262 - Redémarrage après extinction
• F02C 7/277 - Entraînement du rotor pour le démarrage mécanique par une turbine

Abrégé

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Classes IPC  ?

• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
• F01D 25/24 - Carcasses d'enveloppeÉléments de la carcasse, p. ex. diaphragmes, fixations
• F02C 9/16 - Commande du débit du fluide de travail
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales

Abrégé

A gas turbine engine includes a fan and a fan case assembly. The fan includes a fan rotor configured to rotate about an axis of the gas turbine engine and a plurality of fan blades coupled to the fan rotor for rotation therewith. The fan case assembly extends circumferentially around the plurality of fan blades radially outward of the plurality of the fan blades.

Classes IPC  ?

• F04D 29/68 - Lutte contre la cavitation, les tourbillons, le bruit, les vibrations ou phénomènes analoguesÉquilibrage en agissant sur les couches limites
• F01D 11/08 - Prévention ou réduction des pertes internes du fluide énergétique, p. ex. entre étages pour obturations de l'espace entre extrémités d'aubes du rotor et stator
• F01D 11/22 - Réglage actif du jeu d'extrémité des aubes par actionnement mécanique d'éléments du stator ou du rotor, p. ex. par déplacement de sections d'enveloppe par rapport au rotor
• F04D 29/52 - Carters d'enveloppeTubulures pour le fluide énergétique pour pompes axiales

Abrégé

A gas turbine engine includes: an inlet guide vane; an inlet channel extending from a location downstream of the inlet guide vane to a stem manifold; and an outlet channel extending to an outlet port, the outlet port configured to dump anti-ice air overboard, wherein the inlet guide vane includes an anti-ice cavity in fluid communication with the inlet channel and the outlet channel such that anti-ice air, flowing from a downstream location within a core flow of the gas turbine, flows from the inlet channel, through the inlet guide vane, and to the outlet channel.

Classes IPC  ?

• F01D 25/02 - Dispositifs de dégivrage pour machines motrices dans lesquelles se produisent des phénomènes de givrage
• F01D 5/18 - Aubes creusesDispositifs de chauffage, de protection contre l'échauffement ou de refroidissement des aubes
• F02C 7/047 - Chauffage pour prévenir le givrage

Abrégé

A gas turbine engine includes a bypass duct, a heat exchanger, and an inlet shroud. The bypass duct is configured to direct air through a flow path. The heat exchanger is configured to receive a portion of the air flowing through the flow path of the bypass duct. The inlet shroud is coupled with the heat exchanger and configured to adjust a direction of the portion of the air entering the heat exchanger.

Classes IPC  ?

• F02C 7/18 - Refroidissement des ensembles fonctionnels caractérisé par l'agent refroidisseur l'agent refroidisseur étant gazeux, p. ex. l'air
• F01D 25/12 - Refroidissement
• F02C 7/04 - Entrées d'air pour ensembles fonctionnels de turbines à gaz ou de propulsion par réaction
• F02C 9/18 - Commande du débit du fluide de travail par prélèvement, par bipasse ou par action sur des raccordements variables du fluide de travail entre des turbines ou des compresseurs ou entre leurs étages

Abrégé

A heat exchanger may include a first coolant path for circulating a first coolant and a second coolant path for circulating a second coolant, where the first coolant path including a plurality of first cooling tubes, where the second coolant path including a plurality of second cooling tubes, where the first coolant path is fluidly isolated from the second coolant path in the heat exchanger, and where the first cooling tubes and the second cooling tubes are arranged in series and such that the first cooling tubes alternate with the second cooling tubes in an airflow direction.

Classes IPC  ?

• F28D 1/04 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes pour une seule des sources de potentiel calorifique, les deux sources étant en contact chacune avec un côté de la paroi de la canalisation, dans lesquels l'autre source de potentiel calorifique est une grande masse de fluide, p. ex. radiateurs domestiques ou de moteur de voiture avec des canalisations d'échange de chaleur immergées dans la masse du fluide avec canalisations tubulaires
• F28D 7/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations tubulaires fixes pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
• F28D 9/00 - Appareils échangeurs de chaleur comportant des ensembles de canalisations fixes en forme de plaques ou de laminés pour les deux sources de potentiel calorifique, ces sources étant en contact chacune avec un côté de la paroi d'une canalisation
• F28D 21/00 - Appareils échangeurs de chaleur non couverts par l'un des groupes

Abrégé

A cooling system for an electronics cabinet includes a controller configured to operate at least one of a pump or a condenser of a two-phase cooling loop. The cooling system includes a high temperature mode where the setpoint is set to a high setpoint setting, and a low temperature mode where the setpoint is set to a low setpoint setting. The controller is configured to select between the high temperature mode and the low temperature mode based on an evaluation of a power outage.

Classes IPC  ?

• H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage

Abrégé

An infrared suppressor adapted for use with a gas turbine engine includes a first ring arranged circumferentially around a central axis, a second ring arranged circumferentially around the central axis, and a strut that extends radially between and interconnects the first ring and the second ring. A portion of the second ring extends radially toward the first ring such that the portion of the second ring cooperates with the first ring to block line-of-sight into the infrared suppressor.

Classes IPC  ?

• F02K 1/82 - Parois des tubulures de jet, p. ex. chemises

Abrégé

An example system includes a first gas-turbine engine configured to propel an aircraft, the first gas-turbine engine comprising a first electric starter, the first electric starter configured to rotate a spool of the first gas-turbine engine; and one or more controllers collectively configured to: cause, following operation of the first gas-turbine engine, the first electric starter to perform barring of the first gas-turbine engine; measure, during the barring of the first gas-turbine engine, values of one or more parameters of the first gas-turbine engine; and determine, based on the values of the one or more parameters, whether the first electric starter is available for use in performing mid-air restart of the first gas-turbine engine.

Classes IPC  ?

• F02C 7/268 - Entraînement du rotor pour le démarrage
• F01D 19/00 - Démarrage des "machines" ou machines motricesDispositifs de régulation, de commande ou de sécurité en rapport avec les organes de démarrage

Abrégé

A method of forming a ceramic matrix composite having a smooth surface includes laying up a plurality of plies, where some or all of the plies include an arrangement of spread tows comprising carbon fibers, thereby forming a fiber preform. Each spread tow has a height-to-width aspect ratio of less than about 0.1. The fiber preform is infiltrated with a ceramic matrix material and/or ceramic matrix precursor to embed the carbon fibers in a ceramic matrix. Thus, a ceramic matrix composite comprising a smooth and/or flat surface devoid of undulations from rounded tows is formed.

Classes IPC  ?

• C04B 35/80 - Fibres, filaments, "whiskers", paillettes ou analogues
• C04B 35/565 - Produits céramiques mis en forme, caractérisés par leur compositionCompositions céramiquesTraitement de poudres de composés inorganiques préalablement à la fabrication de produits céramiques à base de non oxydes à base de carbures à base de carbure de silicium
• C04B 41/00 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle
• C04B 41/91 - Post-traitement des mortiers, du béton, de la pierre artificielle ou des céramiquesTraitement de la pierre naturelle de céramiques uniquement impliquant l'enlèvement d'une partie des matières des objets traités, p. ex. par attaque chimique

Abrégé

A power electronic assembly includes a power electronic and a cold plate. The power electronic is configured to be powered by electric energy and to generate waste heat from the electric energy. The cold plate include polymeric material and is configured to elastically deform to uniformly cover the power electronic and transfer away the waste heat generated by the power electronic.

Classes IPC  ?

• H05K 7/20 - Modifications en vue de faciliter la réfrigération, l'aération ou le chauffage
• H01L 23/40 - Supports ou moyens de fixation pour les dispositifs de refroidissement ou de chauffage amovibles
• H01L 23/473 - Dispositions pour le refroidissement, le chauffage, la ventilation ou la compensation de la température impliquant le transfert de chaleur par des fluides en circulation par une circulation de liquides

Abrégé

A multi-piece radial turbine rotor includes a hub, turbine blades, and an intermediate ring that couples the turbine blades to the hub. Joints between the components of the rotor are adapted for inspection during manufacture to identify potential defects in the joints.

Classes IPC  ?

• F01D 5/04 - Organes de support des aubes, p. ex. rotors pour "machines" ou machines à flux radial
• B23K 1/00 - Brasage ou débrasage
• F01D 5/30 - Fixation des aubes au rotorPieds de pales